Airworthiness Directives; Airbus Airplanes, 51083-51088 [2014-19708]

Download as PDF Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations (3) Task 55–21–27–960–802 of the Canadair Regional Jet Model CL–600–2B19 Aircraft Maintenance Manual, CSP A–001, Revision 49, dated May 10, 2014. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. mstockstill on DSK4VPTVN1PROD with RULES (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–04, dated January 13, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations. gov/#!documentDetail;D=FAA-2014-01750002. (2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 601R–55– 008, Revision B, dated March 12, 2014. (ii) Reserved. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For VerDate Mar<15>2010 17:33 Aug 26, 2014 Jkt 232001 information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 15, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–19976 Filed 8–26–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–AD; Amendment 39–17937; AD 2014–16–13] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. This AD requires revising the maintenance or inspection program, as applicable, to include the new life limits. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. DATES: This AD becomes effective October 1, 2014. ADDRESSES: You may examine the AD docket on the Internet at http://www. regulations.gov/#!docketDetail;D=FAA2014-0236 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; SUMMARY: PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 51083 Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 series airplanes. The NPRM published in the Federal Register on April 17, 2014 (79 FR 21651). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0210, dated September 11, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition all Airbus Model A300 series airplanes. The MCAI states: Some life limits previously defined in Revision 00 of A300 ALS [airworthiness limitations section] Part 1 have been removed [from] that document at Revision 01 and should normally be included in an ALS Part 4. At this time, there are no plans to issue an ALS Part 4 for A300 aeroplanes. Nevertheless, failure to comply with these life limits could result in an unsafe condition. For the reasons described above, it has been decided to require the application of these life limits through a separate [EASA] AD. Consequently, this [EASA] AD requires application of life limits applicable to Main Landing Gear (MLG) barrel assembly, retraction actuator assembly linkage assembly and flanged duct which were previously contained in Airbus ALS Part 1 Revision 00. EASA AD 2007–0293 [which corresponds with FAA AD 2009–18–15, Amendment 39– 16011 (74 FR 48143, September 22, 2009)], which required compliance with the actions specified in ALS Part 1, will be superseded by a new [EASA] AD, requiring compliance with ALS Part 1 at Revision 1. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/#!documentDetail; D=FAA-2014-0236-0002. Comments We gave the public the opportunity to participate in developing this AD. We E:\FR\FM\27AUR1.SGM 27AUR1 51084 Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES received no comments on the NPRM (79 FR 21651, April 17, 2014) or on the determination of the cost to the public. ‘‘Contacting the Manufacturer’’ Paragraph in This AD Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD. We have become aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an ADmandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Airbus’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the VerDate Mar<15>2010 17:33 Aug 26, 2014 Jkt 232001 recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘design approval holder (DAH) with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH throughout this AD. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 21651, April 17, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 21651, April 17, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 7 airplanes of U.S. registry. We also estimate that it takes about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $595, or $85 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations. gov/#!docketDetail;D=FAA-2014-0236; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\27AUR1.SGM 27AUR1 Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–16–13 Airbus: Amendment 39–17937. Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–AD. (a) Effective Date This AD becomes effective October 1, 2014. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 103, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear; and 36, Pneumatic. (e) Reason This AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. mstockstill on DSK4VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Mar<15>2010 17:33 Aug 26, 2014 Jkt 232001 (g) Revise the Maintenance or Inspection Program Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the life limits specified in Appendix 1 of this AD into the Airbus A300 Airworthiness Limitations Section (ALS) Part 1. The initial compliance time for the replacement is identified in Appendix 1 of this AD and is prior to the applicable life limits specified in Appendix 1 of this AD, or within 90 days after the effective date of this AD, whichever occurs later. (h) No Alternative Actions and Intervals After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (i)(1) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 51085 Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0210, dated September 11, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/# !documentDetailD=FAA-2014-0236-0002. (k) Material Incorporated by Reference None. E:\FR\FM\27AUR1.SGM 27AUR1 mstockstill on DSK4VPTVN1PROD with RULES 51086 VerDate Mar<15>2010 Linkage, and Flange Duct Jkt 232001 (*) Whichever occurs first. Notes are located under the assy title. LIFE LIMITS (*) LIFE LIMITS APPLICABILITY PO 00000 Frm 00020 82-320 B4-2C B4-1xx B4-2xx C4-203 F4-203 N/A X X X X 76600 N/A X X X X 76600 N/A X X X X FH LOG Cal. C66277-10 N/A 66600 C66277-12 N/A C66277-14 N/A Part Number B2-1A B2-1C B2K-3C B2-20x ATA32-10-00 MAIN LANDING GEAR BARREL ASSEMBLY Stirrup Fmt 4700 058303-1 Stirrup pin N/A 76600 N/A X X X X C66457 N/A 76600 N/A X X X X Sfmt 4725 048939 N/A 76600 N/A X X X X 048939-1 N/A 76600 N/A X X X X E:\FR\FM\27AUR1.SGM 058314-1 N/A 76600 N/A X X X X C66279 N/A 76600 N/A X X X X C66279-2 N/A 76600 N/A X X X X C66279-6 Universal joint N/A 76600 N/A X X X X X X X X N/A X X N/A 76600 N/A X X ' N/A 76600 N/A N/A 53300 N/A X X . C61638-10 X X N/A 53300 N/A C61638-20 ER27AU14.000</GPH> N/A 76600 C61637-12 Tie rod 76600 N/A C61637-11 Plate (Rear head end) N/A C61637-10 C61638-11 27AUR1 058313-1 Plate (Upper end) N/A 76600 N/A X X X X C68523-3 N/A 76600 N/A X X Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 17:33 Aug 26, 2014 Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction Actuator Assembly mstockstill on DSK4VPTVN1PROD with RULES VerDate Mar<15>2010 Linkage, and Flange Duct (continued) Jkt 232001 (*) Whichever occurs first. Notes are located under the assy title. PO 00000 Part Number LIFE LIMITS (*) FH LDG LIFE LIMITS APPLICABILITY Frm 00021 Cal. B2-1A B2-1C B2K-3C B2-20x N/A X X X 82-320 B4-2C B4-1xx B4-2xx C4-203 F4-203 X RETRACTION ACTUATOR ASSEMBLY (1) When SB A300-32-0123 embodied before SB A300-32-0113. (2) When SB A300-32-0123 embodied after SB A300-32-0113. Sliding rod C69028-1 N/A 34 000 Fmt 4700 34 000 N/A 32 000 N/A X X X X N/A 32 000 N/A X X X X C69029-3 N/A 32 000 N/A X X X X C69029-4 (2) N/A 22 000 N/A X X X X E:\FR\FM\27AUR1.SGM End fitting 27AUR1 Upper multiple link pin (Multiple link/Upper link) N/A N/A C69029-2 Sfmt 4725 C69028-4 C69029-1 (1) C67078 N/A 33 000 N/A X X X X C67078-1 N/A 33 000 N/A X X X X C61342-4 N/A 36 700 N/A C66510-4 N/A 32 000 N/A X X X X C61505 Piston N/A 76 600 N/A X X X X X LINKAGE ASSEMBLY X C61505-1 N/A 76 600 N/A X X C61505-20 N/A 76 600 N/A X X ATA36-11-05 PNEUMATIC (1) "xx" at the end of the P/N stands for any number between 00 and 99. Duct flanged ( 1) A2127 4063000xx N/A 24 000 N/A X Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations 17:33 Aug 26, 2014 Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction Actuator Assembly 51087 ER27AU14.001</GPH> 51088 Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations Issued in Renton, Washington, on August 4, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–19708 Filed 8–26–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0616; Directorate Identifier 2014–CE–018–AD; Amendment 39–17954; AD 2014–17–01] Examining the AD Docket RIN 2120–AA64 Airworthiness Directives; Viking Air Limited Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC–3 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as looseness of the horizontal stabilizer actuator mounting block in the forward-aft and side-to-side directions. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective September 16, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 16, 2014. We must receive comments on this AD by October 14, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:33 Aug 26, 2014 Jkt 232001 For service information identified in this AD, contact Viking Air Limited Technical Support, 1959 De Havilland Way, Sidney, British Columbia, Canada, V8L 5V5; Fax: 250–656–0673; telephone: (North America) 1–800–663– 8444; email: technical.support@ vikingair.com; Internet: http://www. vikingair.com/content.aspx?id=358. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0616; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Safety Enginer, FAA, New York Aircraft Certification Office, 1600 Steward Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228–7318; fax: (516) 794–5531; email: cesar.gomez@faa.gov. SUPPLEMENTARY INFORMATION: Discussion Transport Canada, which is the aviation authority for Canada, has issued AD No. CF–2014–14, dated June 5, 2014 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for Viking Air Limited Model DHC–3 airplanes. The MCAI states: A horizontal stabilizer actuator (trim jack) mounting block, part number C3FS79–5, was found loose in the forward-aft and side-toside directions. The trim jack mounting block fastens the stabilizer actuator (trim jack) which allows the angle of incidence of the stabilizer to be varied. The stabilizer actuator (trim jack) also functions as the rear mounting point for the stabilizer. Failure of the mounting block through breakage or detachment may cause loss of control of the horizontal stabilizer and subsequent loss of control of the aeroplane. Therefore, this AD mandates a one-time inspection of the stabilizer actuator (trim jack) mounting block. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0616. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Relevant Service Information Viking Air Limited has issued Viking Service Bulletin No. V3/0005, Revision ‘A’, dated May 27, 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Interim Action We consider this AD interim action. After the State of Design reviews and evaluates the reporting data, we may take further rulemaking action in the future. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because failure of the mounting block through breakage or detachment may cause loss of control of horizontal stabilizer and subsequent loss of control. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0616; Directorate Identifier 2014–CE–018– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may E:\FR\FM\27AUR1.SGM 27AUR1

Agencies

[Federal Register Volume 79, Number 166 (Wednesday, August 27, 2014)]
[Rules and Regulations]
[Pages 51083-51088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-19708]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0236; Directorate Identifier 2013-NM-184-AD; 
Amendment 39-17937; AD 2014-16-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This AD was prompted by our 
determination of the need to incorporate new life limits for the main 
landing gear (MLG) barrel assembly, retraction actuator assembly 
linkage, and flange duct. This AD requires revising the maintenance or 
inspection program, as applicable, to include the new life limits. We 
are issuing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

DATES: This AD becomes effective October 1, 2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0236 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM 116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A300 
series airplanes. The NPRM published in the Federal Register on April 
17, 2014 (79 FR 21651).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0210, dated September 11, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition all Airbus Model A300 
series airplanes. The MCAI states:

    Some life limits previously defined in Revision 00 of A300 ALS 
[airworthiness limitations section] Part 1 have been removed [from] 
that document at Revision 01 and should normally be included in an 
ALS Part 4.
    At this time, there are no plans to issue an ALS Part 4 for A300 
aeroplanes.
    Nevertheless, failure to comply with these life limits could 
result in an unsafe condition.
    For the reasons described above, it has been decided to require 
the application of these life limits through a separate [EASA] AD. 
Consequently, this [EASA] AD requires application of life limits 
applicable to Main Landing Gear (MLG) barrel assembly, retraction 
actuator assembly linkage assembly and flanged duct which were 
previously contained in Airbus ALS Part 1 Revision 00.
    EASA AD 2007-0293 [which corresponds with FAA AD 2009-18-15, 
Amendment 39-16011 (74 FR 48143, September 22, 2009)], which 
required compliance with the actions specified in ALS Part 1, will 
be superseded by a new [EASA] AD, requiring compliance with ALS Part 
1 at Revision 1.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0236-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We

[[Page 51084]]

received no comments on the NPRM (79 FR 21651, April 17, 2014) or on 
the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's 
EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this AD.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 21651, April 17, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 21651, April 17, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 7 airplanes of U.S. registry.
    We also estimate that it takes about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $595, or $85 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0236; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 51085]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-16-13 Airbus: Amendment 39-17937. Docket No. FAA-2014-0236; 
Directorate Identifier 2013-NM-184-AD.

(a) Effective Date

    This AD becomes effective October 1, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear; and 36, Pneumatic.

(e) Reason

    This AD was prompted by our determination of the need to 
incorporate new life limits for the main landing gear (MLG) barrel 
assembly, retraction actuator assembly linkage, and flange duct. We 
are issuing this AD to prevent reduced structural integrity of the 
airplane and possible loss of controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Revise the Maintenance or Inspection Program

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
life limits specified in Appendix 1 of this AD into the Airbus A300 
Airworthiness Limitations Section (ALS) Part 1. The initial 
compliance time for the replacement is identified in Appendix 1 of 
this AD and is prior to the applicable life limits specified in 
Appendix 1 of this AD, or within 90 days after the effective date of 
this AD, whichever occurs later.

(h) No Alternative Actions and Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (i)(1) of this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2013-0210, 
dated September 11, 2013, for related information. This MCAI may be 
found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetailD=FAA-2014-0236-0002.

(k) Material Incorporated by Reference

    None.

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[GRAPHIC] [TIFF OMITTED] TR27AU14.000


[[Page 51087]]


[GRAPHIC] [TIFF OMITTED] TR27AU14.001



[[Page 51088]]


    Issued in Renton, Washington, on August 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-19708 Filed 8-26-14; 8:45 am]
BILLING CODE 4910-13-P